摘要
为了在满足精度要求的前提下节省月球重力场模型的计算时间,依据Kaula准则分析了目前国际上公认的最精确的两个重力场模型GLGM-2和LP165P,提出了在一定阶次截断重力场模型的问题。通过仿真不同阶次重力场模型作用下轨道高度为50 km的圆形极轨道环月卫星轨道特征的变化,验证了50 km以上高度卫星非球形摄动分析时可以将重力场模型截断至一定阶次的结论,并利用截断至70阶次的重力场模型仿真分析200 km圆轨道卫星一年内轨道下降程度。最后在仿真结果的基础上得到了200 km高度环月卫星需要每50天进行一次轨道保持控制的结论并完成一次轨道保持控制仿真。研究结论可以为我国低轨环月卫星轨道保持提供参考。
The work in this paper deduced time consuming of the computer and reached certain precision when using the lunar gravity model. First, with the globally-accepted lunar gravity models, LP165P and GLGM-2, characters of the lunar gravity models were analyzed based on the Kaula theory. Then, making the use of LP165P models truncated to different orders and degrees, the lunar satellite orbit with 50km height revolution was compared in order to support the idea that lunar gravity model can be truncated appropriately. Meanwhile, the free running time span of lunar satellite with 200km height were given respectively. Last, a maintenance method is presented for a 200km height orbit.
出处
《飞行力学》
CSCD
北大核心
2009年第6期56-59,共4页
Flight Dynamics
